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74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il)
Reynolds number: 500,000
Max Cl/Cd: 116.23 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp2mod-il-500000.txt
Download as CSV file: xf-fx74130wp2mod-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 74-130 WP2 MOD                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1198   0.09603   0.09316  -0.0862   0.8385   0.0133
 -11.000  -0.1762   0.09931   0.09621  -0.0967   0.8458   0.0127
 -10.750  -0.1708   0.09613   0.09304  -0.0980   0.8446   0.0128
 -10.500  -0.1626   0.09367   0.09059  -0.0986   0.8433   0.0134
 -10.250  -0.1576   0.09059   0.08752  -0.1000   0.8419   0.0136
 -10.000  -0.1530   0.08761   0.08455  -0.1013   0.8401   0.0144
  -9.750  -0.1497   0.08434   0.08129  -0.1028   0.8385   0.0148
  -9.500  -0.1468   0.08100   0.07796  -0.1045   0.8370   0.0145
  -9.250  -0.1450   0.07759   0.07455  -0.1062   0.8356   0.0153
  -9.000  -0.1446   0.07394   0.07091  -0.1083   0.8339   0.0160
  -8.750  -0.1459   0.07013   0.06713  -0.1105   0.8320   0.0164
  -8.500  -0.1502   0.06601   0.06306  -0.1135   0.8296   0.0165
  -8.250  -0.1607   0.06159   0.05866  -0.1166   0.8262   0.0168
  -8.000  -0.1741   0.05846   0.05548  -0.1164   0.8226   0.0166
  -7.750  -0.1418   0.04258   0.03964  -0.1106   0.8146   0.0183
  -7.500  -0.1467   0.03932   0.03629  -0.1101   0.8123   0.0183
  -7.250  -0.1491   0.03597   0.03280  -0.1093   0.8101   0.0184
  -7.000  -0.1479   0.03263   0.02929  -0.1084   0.8082   0.0184
  -6.750  -0.1617   0.02544   0.02185  -0.1072   0.8064   0.0190
  -6.500  -0.1551   0.02205   0.01836  -0.1065   0.8046   0.0196
  -6.250  -0.1425   0.01978   0.01602  -0.1060   0.8025   0.0202
  -6.000  -0.1284   0.01763   0.01373  -0.1054   0.8002   0.0209
  -5.750  -0.1125   0.01556   0.01152  -0.1047   0.7980   0.0219
  -5.500  -0.0948   0.01360   0.00934  -0.1040   0.7960   0.0232
  -5.250  -0.0742   0.01196   0.00743  -0.1032   0.7942   0.0253
  -4.250   0.0223   0.01857   0.01232  -0.1057   0.7915   0.0190
  -4.000   0.0470   0.01615   0.00976  -0.1050   0.7893   0.0159
  -3.750   0.0725   0.01488   0.00837  -0.1044   0.7868   0.0158
  -3.500   0.0981   0.01402   0.00743  -0.1039   0.7844   0.0164
  -3.250   0.1238   0.01333   0.00667  -0.1035   0.7822   0.0170
  -3.000   0.1512   0.01312   0.00640  -0.1036   0.7803   0.0183
  -2.750   0.1760   0.01231   0.00549  -0.1031   0.7785   0.0194
  -2.500   0.2011   0.01180   0.00494  -0.1028   0.7760   0.0207
  -2.250   0.2273   0.01145   0.00457  -0.1026   0.7731   0.0247
  -2.000   0.2502   0.01022   0.00412  -0.1025   0.7704   0.2566
  -1.750   0.2687   0.00858   0.00405  -0.1017   0.7679   0.7079
  -1.500   0.2929   0.00894   0.00450  -0.1003   0.7658   0.8071
  -1.250   0.3176   0.00917   0.00471  -0.0992   0.7635   0.8266
  -1.000   0.3400   0.00934   0.00491  -0.0976   0.7598   0.8435
  -0.750   0.3618   0.00951   0.00507  -0.0958   0.7566   0.8608
  -0.500   0.3831   0.00956   0.00511  -0.0939   0.7540   0.8718
  -0.250   0.4080   0.00955   0.00505  -0.0930   0.7518   0.8787
   0.000   0.4328   0.00957   0.00504  -0.0924   0.7488   0.8847
   0.250   0.4593   0.00955   0.00501  -0.0923   0.7448   0.8894
   0.500   0.4849   0.00946   0.00490  -0.0918   0.7415   0.8923
   0.750   0.5129   0.00938   0.00477  -0.0919   0.7388   0.8948
   1.000   0.5414   0.00933   0.00468  -0.0923   0.7360   0.8971
   1.250   0.5683   0.00927   0.00465  -0.0924   0.7311   0.8994
   1.500   0.5975   0.00920   0.00455  -0.0930   0.7274   0.9012
   1.750   0.6280   0.00913   0.00444  -0.0938   0.7244   0.9027
   2.000   0.6544   0.00906   0.00440  -0.0937   0.7201   0.9042
   2.250   0.6814   0.00900   0.00435  -0.0938   0.7154   0.9056
   2.500   0.7098   0.00892   0.00426  -0.0941   0.7117   0.9069
   2.750   0.7378   0.00888   0.00423  -0.0945   0.7074   0.9082
   3.000   0.7651   0.00884   0.00424  -0.0946   0.7019   0.9096
   3.250   0.7939   0.00878   0.00418  -0.0951   0.6977   0.9110
   3.500   0.8218   0.00878   0.00422  -0.0955   0.6925   0.9122
   3.750   0.8500   0.00876   0.00423  -0.0959   0.6869   0.9134
   4.000   0.8789   0.00874   0.00422  -0.0964   0.6817   0.9147
   4.250   0.9061   0.00871   0.00423  -0.0966   0.6730   0.9161
   4.500   0.9327   0.00866   0.00420  -0.0966   0.6622   0.9171
   4.750   0.9580   0.00863   0.00416  -0.0962   0.6493   0.9183
   5.000   0.9826   0.00867   0.00420  -0.0958   0.6350   0.9196
   5.250   1.0071   0.00876   0.00429  -0.0954   0.6223   0.9212
   5.500   1.0303   0.00889   0.00440  -0.0947   0.6064   0.9231
   5.750   1.0527   0.00908   0.00454  -0.0939   0.5880   0.9249
   6.000   1.0763   0.00926   0.00475  -0.0934   0.5740   0.9266
   6.500   1.1210   0.00970   0.00522  -0.0920   0.5383   0.9303
   6.750   1.1372   0.00999   0.00548  -0.0901   0.5097   0.9328
   7.000   1.1472   0.01045   0.00582  -0.0871   0.4649   0.9364
   7.250   1.1354   0.01148   0.00646  -0.0802   0.3836   0.9436
   7.500   1.1192   0.01269   0.00737  -0.0728   0.3222   0.9542
   7.750   1.1116   0.01429   0.00862  -0.0682   0.2498   0.9770
   8.000   1.1084   0.01614   0.01008  -0.0651   0.1793   1.0000
   8.250   1.1070   0.01798   0.01158  -0.0623   0.1195   1.0000
   8.500   1.1093   0.01963   0.01297  -0.0600   0.0754   1.0000
   8.750   1.1154   0.02108   0.01424  -0.0582   0.0486   1.0000
   9.000   1.1260   0.02225   0.01536  -0.0568   0.0367   1.0000
   9.250   1.1378   0.02335   0.01647  -0.0555   0.0292   1.0000
   9.500   1.1465   0.02467   0.01778  -0.0539   0.0226   1.0000
   9.750   1.1574   0.02586   0.01898  -0.0526   0.0175   1.0000
  10.000   1.1640   0.02740   0.02058  -0.0508   0.0131   1.0000
  10.250   1.1715   0.02889   0.02211  -0.0492   0.0108   1.0000
  10.500   1.1686   0.03124   0.02458  -0.0465   0.0097   1.0000
  10.750   1.1782   0.03264   0.02610  -0.0453   0.0093   1.0000
  11.000   1.1856   0.03426   0.02781  -0.0438   0.0088   1.0000
  11.250   1.1925   0.03597   0.02962  -0.0424   0.0085   1.0000
  11.500   1.1993   0.03777   0.03152  -0.0410   0.0081   1.0000
  11.750   1.2076   0.03946   0.03330  -0.0398   0.0077   1.0000
  12.000   1.2162   0.04120   0.03513  -0.0387   0.0075   1.0000
  12.250   1.2255   0.04287   0.03688  -0.0378   0.0071   1.0000
  12.500   1.2343   0.04462   0.03869  -0.0370   0.0068   1.0000
  12.750   1.2416   0.04668   0.04085  -0.0360   0.0065   1.0000
  13.000   1.2491   0.04904   0.04336  -0.0348   0.0063   1.0000
  13.250   1.2583   0.05150   0.04601  -0.0337   0.0062   1.0000
  13.500   1.2652   0.05494   0.04976  -0.0324   0.0061   1.0000
  13.750   1.2667   0.05855   0.05362  -0.0314   0.0061   1.0000
  14.000   1.2659   0.06155   0.05682  -0.0308   0.0060   1.0000
  14.250   1.2627   0.06509   0.06058  -0.0302   0.0060   1.0000
  14.500   1.2558   0.06927   0.06499  -0.0299   0.0060   1.0000
  14.750   1.2460   0.07393   0.06988  -0.0298   0.0059   1.0000
  15.000   1.2344   0.07891   0.07510  -0.0302   0.0059   1.0000
  15.250   1.2183   0.08491   0.08132  -0.0310   0.0060   1.0000
  15.500   1.2013   0.09117   0.08781  -0.0325   0.0060   1.0000
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